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The design of complex systems in the presence of changing requirements, rapidly evolving technologies, and design uncertainty continues to be a challenge. Furthermore, the design of future platforms must take into account the interoperability of a variety of heterogeneous systems and their role in a larger "system-of-systems." To date, methodologies to address the complex interactions and optimize the system at the macro-level have lacked a clear direction and structure and have largely been conducted in an ad-hoc fashion. Traditional optimization has centered around individual vehicles with little regard for the impact on the overall system. A key enabler for reduced cost and cycle time is the ability to rapidly analyze technologies and perform trade studies using a capability-based approach. While many entities have expressed a desire to perform capability-based design, the need for a structured discipline exists. This research will examine how collaboration for the design of such systems-of-systems can be enabled through the use of surrogate models and will demonstrate a top-down analysis methodology for the evaluation of systems and technologies with respect to desired capabilities. A technique for inverse design where any variable can be treated as an independent variable is made routine through the structured use of surrogate models and probability theory. For the testbed demonstration, a depoliticized, notional scenario was postulated to develop a testbed environment in which humanitarian aid and supplies must be delivered to forward-deployed troops for dispersal in a host country under fire.

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In response to the request for proposal (RFP) for the 2003 AIAA Undergraduate Team Engine Design Competition, the FAS Propulsion Design team from the Georgia Institute of Technology presents StarRunner: A Single-Stage-to-Orbit (SSTO), Airbreathing, Hypersonic Propulsion System. Low-cost, highly reliable access to low-Earth orbit (LEO) and the International Space Station (ISS) is an area of continuing research and debate. StarRunner is proposed to supplement a notional Crew Transfer Vehicle through the ability to deliver a 25,000 lb payload to the ISS. The horizontal takeoff/horizontal landing (HTHL) vehicle makes use of a turbine-based combined cycle (TBCC) propulsion system consisting of 14 low-bypass-ratio turbofan engines and a dual-mode ramjet/scramjet propulsion system for high-speed flight. The vehicle also takes advantage of ultra-high-temperature ceramic thermal protection materials and uses hydrogen fuel for regenerative cooling of engine components. StarRunner is compatible with standard runways, with a gross takeoff weight of approximately 1,000,000 lbs, and has a cost per pound to orbit of approximately $825/lb. This advanced, fully reusable space transport vehicle and integrated propulsion system design demonstrates student efforts to understand issues facing the space launch community. Future enabling and enhancing technologies for TBCC SSTO launch vehicles are explored and analyzed. The final StarRunner design addresses and proposes several innovative solutions to traditional problems.